Rocket launchers



Feb. 25, 1964 P, v, CHO'ATE Em, 3,122,059

ROCKET LAUNCHERS 3 Sheets-Sheet 1 Filed NOV. 13, 1961 INVENTORS CHARLESB. WEEKS PAULV. CHOATE 7 mm. m mm ow mm ATTORNEY P. V. CHOATE ETALROCKET LAUNCHERS 3 Sheets-Sheet 2 INVENTSRS CHARLES S. WEEK PAUL V.CHOATE BY ATTORNEI Feb. 25, 1964 Filed Nov. 15, 1961 mom s P. v. CHOATEETAL 3,122,059

Feb. 25, 1964 ROCKET LAUNCHERS 5 Sheets-Sheet 3 Filed NOV. 13, 1961 FIG.I4

FIG. [3

' INVENTO CHARLES B.'WEEKS PAUL V. CHOATE ATTORN EY United States PatentOffice 3,122,659 RQCKET LAUNCHERS Paul V. Choate, Milton, and Charies B.Weeks, Reading, Mass, assignors to Flightex Fabrics, Inc, Pawtucket, RL,a corporation of Rhode Island Filed Nov. 13, 1961, filer. No. 151,894 1tClaims. (Cl. 89-17) The present invention relates to launchers forrockets and particularly to such launchers that have characteristicsenabling each to be manufactured at relatively low cost and to be easilycarried and effectively used by an infantryman against a tank orfortified position and to combinations of rockets with such launchers.

The general objective of the invention is to provide such a launcher andthis objective is attained by providing a launcher comprising a barrelconsisting of first and second tubular sections interconnected totelescope between a shortened, inoperative position .and an extendedoperative position. The firing pin and firing spring are carried by thefirst section that constitutes the breech end of the launcher and thetrigger mechanism is carried by the second section that constitutes themuzzle end of the launcher and is connected to the firing pin by anelement attached to the second section. A trigger controlled release,which includes .a scar, is carried by the second section. A member isconnected to the element and is movable into and out of its engagementwith the sear. The engagement of the movable member With the sear isineffective to move .the firing pin into its cocked position in theinoperative position of the launcher, the cocked firing pin positionthen being established by the extension of the sections to establishsaid operative launcher position.

Another objective of the invention is to provide the element in the formof a cable on a spring wound reel associated with the trigger mechanismand trained about the movable member. The length of the cable is suchthat, if the trigger mechanism is not cocked, extension of the launcherdoes not tension the firing spring as the reel freely unwinds to pay outall the cable during such extension. it the movable member is movedforwardly and engaged by the sear, the cable then becomes fully pulledout before the full extension of the launcher sections so that the cablepulls the firing pin Efiorwardly relative to the first section as theextension of the launcher is completed to establish its operativeposition.

Another objective of the invention is to safeguard further againstaccidental discharge by providing a positive lock preventing movement ofthe firing pin towards the igniter, the lock being releasable only whenthe launcher is in its operative position.

Another objective of the invention is to have sights that enable thelauncher to be used with maximum accuracy and the rear sight and thefront sight are both in protected, inoperative positions while thelauncher is in condition to be carried. Both sights are carried by thesecond or muzzle section of the launcher and are selferecting.

In accordance with this objective, the rear sight is pivoted to swingrearwardly and downwardly from an erect position of use against theaction of an erecting spring into an inoperative position in parallelwith the axis of the launcher sections. The breech or first section hasa forwardly opening housing which receives and holds the free end of therear sight when in its inoperative position, as the sections of thelauncher are telescoped to reestablish its inoperative position.

The front sight is connected to the muzzle end of the first section by aspring hinge to swing transversely of the muzzle and is held in thatposition as by a muzzle or front cover connected to a breech or rearcover by a resilient 3,l22,59 Patented Feb. 25, 1964 connector includingan adjustable carrying sling. The rear cover is locked to the breech endof the launcher by a release pin. The user has but to pull the releasepin and free the rear cover. The front cover and connectorthen fall freeof the launcher and the front sight erects itself. The user then pullsthe breech or first section rearwardly relative to the muzzle or firstsection to extend the launcher into its operative position with the rearsight erecting itself and the firing mechanism becoming cocked.Releasable means are provided to interlock the section in the operativelauncher position.

Another objective of the present invention is to estab lish the launcheras a packing case for carrying a rocket from which it is safe toshoulder fire the rocket and which is suitably water tight to ensurethat moisture cannot enter therein and possibly cause malfunctioning.

Yet another objective is that of providing a rocket and launchercombination in which the rocket is held against forward and rearwardmovement relative to the launcher, whether in its inoperative or itsoperative position, without interference with the launching of therocket when its propellant charge is ignited.

In the accompanying drawing there is shown an illustrative embodiment ofthe invention from which these and other of its objectives, novelfeatures, and advantages will be readily apparent.

In the drawings,

FIGURE 1 is a side elevation of the rocket launcher in its shortened,inoperative position,

FIGURE 2 is a like view of the rocket launcher in its extended,operative position,

FIGURE 3 is a section, on an increased scale, taken approximately alongthe indicated lines 3-3 of FIG- URE 2.

FIGURE 4 is a fragmentary section, on an increased scale, through thefiring pin housing and the rear of the breech section to show aprojectile locked therein against unintended forward movement,

FIGURE 5 is a fragmentary view of the muzzle end of the second launchersection with the front sight shown in its erected position,

FIGURE 6 is a section taken approximately along the indicated lines 66of FIGURE 5,

FIGURE 7 is a vertical section through the trigger mechanism housing,

FIGURE 8 is an exploded view showing the main parts thereof inperspective,

FIGURE 9 is a section taken vertically through the rear sight,

FIGURE 10 is a front View of the rear sight with its cap removed,

FIGURE 11 is a view of the breech end of the launcher with the rearcover in place,

FIGURE 12 is a fragmentary elevational view of the undersurface of thelauncher showing certain details of the connector for the covers,

FIGURE 13 is an elevational view of a lock for holding a rocket againstforward movement, and

FIGURE 14 is a fragmentary, horizontal section through the firing pinhousing showing the lock against accidental rearward movement of thefiring pin.

In accordance with the invention, a rocket launcher comprises first andsecond tubular sections 20 and 241. The section 20 is the breech sectionand slidably fits within the section 21 which is the muzzle section andis shorter than the latter so that its forward end presents an annularshoulder 22.

The section Ztl has at least one lengthwise diametrically opposed,groove 23 which terminates short of its ends and receives a pin 24extending through an opening 25a in the band 25 on the rear end of thesection 11. The pin 24 is fixed to the rear end of an arm 26 whoseforward end is urged outwardly by a spring 27 back by the mount 23 towhich the arm 26 is pivoted as at 29, see FIGURE 3. At the forward endof the mount 28 there is a pivot 39 supporting a release 31 yieldablyurged by a spring 32 to position its shoulder .33 under the arm 26 toblock its movement against the action of the spring 27 thus to preventthe pin 24 from moving outwardly under the load exerted thereon duringfiring. The spring 32 also urges the end of the release 31 upwardlybetween the forked ends 26a of the arm 26 so that on manual engagement,the shoulder 33 is moved forwardly out of its position in which movementof the arm 26 is blocked. A thin strip 34 is attached to the arm 26 andoverlies the release 31 so that when the forward portion of the boot 35,sealed to the tube 2.1 to prevent water leakage, is pressed inwardly,disengagement of the release 31 and actuation of the arm 26 will resultto move the pin 24 outwardly. When the launcher sections and 21 havebeen pulled apart to the maximum extent, the spring actuated pin 24-enters into a depression 23A at the front end of the groove 13 thus tolock the rocket sections in their extended position as is necessary foruse of the launcher while permitting them to be released so that therocket sections may be again telescoped. An O-ring 36 is located betweenthe band and the band 37 fast on the rear end of the rocket breechsection 2i).

The upper surface of the section 21 also is provided with a generallyindicated, trigger mechanism housing 38, and between the rearrnost band39 and the band 25 there is a channel 40 on the lower surface of thesection 21. An arm 41 is pivotably connected to the rear of the channel40, supporting, at right angles, the rear cover 42 which is providedwith a compressible seal face 43 and adjacent which there aretransversely disposed channels 44, see FIGURES 1 and 11.

In practice, a cover 45 having a compressible seal face 46 for themuzzle end of the section 21 has a yoke 4-7 pivotally connected theretoat diametrically spaced zones and dimensioned so that it may straddlethe muzzle end with its closed end against or close to the section 21. Ametal strap 48 is pivoted to the yoke 47 and connected to a rear section49 by a resilient section consisting of parallel springs St The rearsection 49 has a hook 52 disposed to be caught in the channels 44. Thecovers 42 and 45 are thus tensioned against the breech and muzzle endsof the inoperatively positioned launcher section and locked in thatposition by providing the cover 42 with an apertured tab 53 fitting overa rearwardly disposed projection 54 of the firing pin housing cover 54a.ceivcs the keeper pin 55. An adjustable carrying sling 56 is attached tothe yoke 47 and to the rear section 49 of the connector.

With this construction, the rocket launcher may be conveniently carriedin its shorted, inoperative position and quickly prepared for use bypulling the pin and disengaging the cover tab 53 from the projection 54and swinging the rear cover away therefrom. The front cover 45, thestrap 58 and its sections 49 and 50 fall free While the rear cover 4-2swings downwardly out of the way. The launcher sections may then beextended for use as by holding the section 21 with one hand and pullingthe section 20 by means of the loop 57 carried by the band 37 until thepin 24 interlocks the sections when the operalive launcher position isestablished, as above described.

The band 37 supports a forwardly extending housing 53 which is spaced soas not to interfere with movement of the section 21. A receiver 59,having a forwardly disposed opening, is mounted on the housing 58. Inthe inoperative position of the launcher sections, the receiver 59houses the end of a generally indicated rear sight 6d which is pivotedas at 61 between arms 62 of a mount 63 attached to the rear of thehousing 33 and urged into an erect position by a spring 64 against astop 65 which the rearward edge of the mount 63 provides. As the rocketThe projection 54 has a transverse bore which re- 1 sections areextended, the rear sight is freed to erect itself into its position ofuse.

It will be noted that there is a band 66 adjacent the front end of thesection 21. The band 66 has spaced cars 67 for the pivot 63 of agenerally indicated front sight 69 which is biased upwardly into anerect position of use by the spring 6%. The front sight 69 includes amount 70 which receives the pivot 63 and carries a clear plastic sheet71 and a seal 72, the pivot enabling the front sight to be pivotedforwardly into its inoperative position. The front sight 69 in itsinoperative position, see FIG- URE 1, has its sheet 7 1 held by thefront cover 45 within the muzzle end of the section 21, which is notchedas at 73 for that purpose, the space, when the sight is so positioned,being sealed by the seal 72. When the front cover 45 falls free, asabove described, the spring 69a erects the front sight 69, with themount '76 seated against the section 11 to provide a positive positionof use.

It will be noted that the sheet 70 has a central vertical line 74 withvertically spaced, transverse graduations 75 marked thereon and that thetarget is visible therethrough, the graduations 75 decreasing in lengthas the indicated target distance increases. Markings 76 are alsoprovided to assist the firer in leading moving targets.

The rear sight 60, see FIGURES 9 and 10, is shown as consisting of amember '78 of U-shaped cross section and having upper and lower openings79 and 8%, respectively. A strip 8?. is clamped thereto as by bolts 82passins through anchoring strips 33 with the strip 81 having verticallydisposed slots 84 enabling the strip 81 to be adjusted verticallyrelative to the channel 78. The strip 81 is provided with a pair ofsight holes 35 and a pair of transverse, detent slots 3%. A slide 8'7 iscarried by the channel 73 and has a resilient detent arm 88 engageablewith either slot 36 to then bring its slot 39 into registry with theappropriate one of the sight holes 85. In practice, the upper end of thesight is protected by a protective, safety rubber cap 90 having alinedwindows 91 in its front and back walls and used to prevent any chance ofthe user being injured by contact with the rear sight 6% while sightingand firing the launcher.

The rear sight 6% is important to accuracy when its projectile, thegenerally indicated rocket 92, is powered by solid fuel as variations inperformance result with the temperature. A higher trajectory isattendant cold weather so that the upper sight hole is then used.

It will be noted that the rocket 92 has an intermediate shoulder 93engageable with the shoulder 22 and thereby held against rearwardmovement, and that its rear part, see FIGURE 4, including its folded,pivoted fins 94, which are urged outwardly in flight by springs 95, ishoused wholly by the section 2%. In practice, it is desirable to preventthe rocket 92 from moving forwardly unless fired. To that end, seeFIGURES 4 and 13, a lock is provided that is apertured at 97 to beanchored by an attached fin Q4. The lock 6 is formed from a metal stripand has an intermediate twist 93 so that the rear end 9 9 may passthrough a slot 1% in the rear cover 42, the rear end 99 having a stop161 engageable with the rear cover 54a of the firing pin housing 58. Inpractice, the keeper pin 55, for locking the rear cover 42, includes aparallel pin 55a for entry through the hole QM in the exposed lock end99. When the pins 55 and 55a are removed, the launcher may be extendedinto its op erative position and while the rocket is secured by the lock96 in its launcher against forward movement, the thrust of its ignitedcharge is great enough to readily bend the lock 96 and its stop 1M thusto free it.

It will be noted from FIGURE 4 that the housing 58 receives the cap N2of a projectile igniter whose tube 1G3 extends downwardly through apassage 164 for connection with the main igniter of the motor (notshown) of the rocket 92. A firing pin 1%5, which may best be seen inFIGURE 4, is urged forwardly in a bore by a spring 107, held within thehousing and the forward end of the pin 105 is connected to a cable 1438extending forwardly into the trigger housing 38 where it passes over anelement 109 in the form of an idler roller, see FIGURES 7 and 8. Thecable 1% is fastened to a reel 116 rendered self-winding by means of thesprings 111. The firing pin 105 is shown as having at its rear end, ataper 1415a and a contact portion 1fiSb at its extremity for strikingthe igniter cap 102.

The roller 109 is confined in transversely alined guideways 112 in thehousing 38 each having an inturned flange 113 overlying a slidableroller guide 114 for the slidable cocking actuator 115. The cockingactuator has ears 116 for engaging the roller 109 and is moved forwardlyagainst the action of its return spring 117 by means of the rod 118which passes forwardly through the seal 119 and provided with a grip 11%for manual engagement by the user. The forward end 120 of the guide 114and of the guideways 112 and the ears 116 are upwardly inclined so thatin its forward position, the roller 1199 is raised ahead of and blockedagainst rearward movement by the sear 121 which is pivoted at 122adjacent its rear end. It will be noted that the actuator 115 has atransverse pin 115a between the shoulders 114a of the guide 114 by whichthe guide 114 is moved forwardly slightly to permit the positioning ofthe roller 109 ahead of the sear 121 and by which the guide 114 is againmoved forwardly when the grip 119a is released to permit the spring 117to operate.

The forward end of the sear 121 is connected as at 123 to a trigger 124pivoted at 125 between its ends and covered with a protective,waterproof boot 126. When the rearward portion of the trigger 124 isdepressed, the sear 121 is raised to release the roller Hi9 which isthen driven rearwardly by the firing pin spring 1417 unless the safety127 is in its rearward position blocking sear movement. The safety 127has a pull rod 128 extending through the seal 119 and terminating in ahandle 129. In practice, a detent 136 is provided yieldably resistingmovement of the safety 127 from either of its positions.

The length of the cable 1118 is such that when the launcher is extendedinto its operative position with the roller 11 9 in the positionillustrated by full lines in FIG- URE 7, the firing pin 1135 is notmoved to load the firing pin spring 1117. If, however, the roller 1% isretained forwardly, in its dotted line position, by the sear 121, whenthe launcher is thus extended, the length of the cable is such that thefiring pin spring 1537 becomes fully loaded and the firing pin 105 ismoved forwardly relative to the rear section into its cocked position.It is possible that should the roller 1119 be in its full line positionseated against the cocking actuator ears 116, it could be pulledforwardly manually but the spring 1117 is of such strength that the riskof the actuator rod 118 slipping from the users grasp, with aconsequential accidental release of the firing pin 1115, is great.

Such an accident is prevented by means of a removable locking pin 131which is inserted in a bore 132 in the fir ing pin housing 38, seeFIGURES 4 and 7. The pin 131 has a pivoted end 133 so that it isoperative to engage the taper 1515a and to force the firing pin 105forwardly. The pin 131 is also provided with an annular groove 134 whichreceives the end of the pin 105 so that it becomes locked againstremoval until the firing pin 105 is in its cocked position which, asabove indicated, is possible only when the launcher is in its extended,operative position.

We claim:

1. In a rocket launcher, first and second tubular sections connected totelescope between a shortened, inoperative position and an extended,operative position, one end of said first section being the breech endof the launcher, and means for firing a rocket positioned in saidlauncher, said means including a firing pin and a firing spring carriedby said first section, said firing spring being connected to said pin tobe loaded by movement of said firing pin into its cocked position, andan element connected to said pin, means connecting said element to saidsecond section; a trigger controlled release including a sear carried bysaid second section, and a movable member connected to said element andoperative to effect its engagement with said sear, the engagement ofsaid movable member with said sear being ineffective to move said firingpin into its cocked position in the inoperative position of saidlauncher, said firing pin being then cocked by the extension of saidsections to establish said operative launcher position.

2. In a rocket launcher, first and second tubular sections connected totelescope between a shortened, inoperative position and an extended,operative position, one end of said first section being the breech endof the launcher, and means for firing a rocket positioned in saidlauncher, said means including a firing pin and a firing spring carriedby said first section, said firing spring being connected to said pin tobe loaded by movement of said firing pin into its cocked position, and acable connected to said pin, a spring wound reel carried by said secondsection to which said cable is connected, the payed-out length of saidcable being insufiicient to move said pin during the extension of saidsections into said operative launcher position, trigger controlledmechanism carried by said second section and including a scar, a membermovable relative thereto in a direction lengthwise of said section, saidcable being trained about said member, said member, in its forwardposition, being engageable by said sear and then so shortening theeffective length of said cable as to cause the extension of saidlauncher sections into its operative position to move said pin into itscocked position thus to load said firing spring, and trigger controlledmeans connected to said sear to disengage it from said member.

3. In a rocket launcher, first and second tubular sections connected totelescope between a shortened, inoperative position and an extended,operative position, one end of said first section being the breech endof the launcher, and means for firing a rocket positioned in saidlauncher, said means inciuding a firing pin and a firing spring carriedby said first section, said firing spring being connected to said pin tobe loaded by movement of said firing pin into its cocked position, and acable connected to said pin, a spring wound reel carried by said secondsection to which said cable is connected, the payed-out length of saidcable being insufiicient to move said pin during the extension of saidsections into said operative launcher position, trigger controlledmechanism carried by said second section and including a scar andresilient means urging said sear into a first position, a member movablerelative thereto in a direction lengthwise of said second section, saidcable being trained about said member, said member, in its forwardposition, being engageable by said sear when said sear is in its firstposition and then so shortening the effective length of said cable as tocause the extension of said launcher sections into its operativeposition to move said pin into its cocked position thus to load saidfiring spring, and a manually movable actuator including a stop andmovable between a rearward position and a forward position, a springyieldably holding said actuator in said rearward position, said memberbeing in engagement with said stop unless said member is in engagementwith said sear, in the forward position of said actuator, said memberbeing positioned for engagement by said sear in said first searposition, and trigger controlled means connected to said sear to move itfrom said first position into a second position in which it isdisengaged from said member.

4. In a rocket launcher, first and second tubular sections connected totelescope between a shortened, inoperative position and an extended,operative position, one end of said first section being the breech endof the launcher, and means for firing a rocket positioned in saidlauncher, said means including a firing pin and a firing spring carriedby said first section, said firing spring being connected to said pin tobe loaded by movement of said firing pin into its cocked position, and acable connected to said pin, a spring wound reel carried by said secondsection to which said cable is connected, the paye -out length of saidcable being insufficient to move said pin during the extension of saidsections into said operative launcher position, trigger controlledmechanism carried by said second section and including a scar andresilient means ur'ing said sear into a first position, a member movablerelative thereto a direction lengthwise of said second section, saidcable being trained about said memher, said member, in its forwardposition, bel engageable by said sear when said sear is in its firstposition and then so shortening the eifective length of said cable as tocause the extension of said launcher sections into its operativeposition to move said pin into its cocled position thus to load saidfiring spring, and trigger controlled means connected to said sear tomove it from said first position into a second position in which it isdisengaged from said member, and a safety movable between a firingposition and a safe position in which it engages and blocks movement ofsaid scar from its first position.

5. In a rocket launcher, first and second tubular sections connected totelescope between a shortened, inoperative position and an extended,operative position, one end of said first section being the breech endof the launcher, and means for firing a rocket positioned in saidlauncher, said means including a firing pin and a firing spring carriedby said first section, said firing spring being connected to said pin tobe loaded by movement of said firing pin into its cocked pos ion, and acable connected to said pin, a housing carried by said second section, aspring Wound reel within said housing, the payed-out length of saidcable being insufiicient to move said pin during the extension of saidsections into said operative launcher position, trigger controlledmechanism carried by said housing and including a scar resiliently urgedinto a first position, a member supported by said housing for movementthereto in a direction lengthwise of said second section, said cablebeing trained about said member, said member, in its forward position,being engageable by said sear when said sear is in its first positionand then so shortening the effective length of said cable as to causethe extension of said launcher sections into its operative position tomove said pin into its cocked position and to load said firing spring,and trigger controlled means connected to said sear move it from said A"at position into a second position in which it is disengaged from saidmember.

6. In a rocket launcher, first and second tubular sections connected totelescope between a shortened, inoperative position and an extended,operative position, one end of said first section being the breech endof the launcher, and means for firing a rocket positioned in saidlauncher, said means including a firing pin having a tapered rearportion and a firing spring carried by said first section, said firingspring being connected to said pin to be loaded by forward movement ofsaid firing pin from a rearward position into its cocked position, and alock transversely movable relative to the path of said firing pin, saidloclr including a tapered end operable to engage said tapered pinportion and force it forwardly from said rearward position, said lockalso having an intermediate pin engaging recess, and a connectionbetween said pin and said second section including a member movablebetween forward and rearward positions, said firing pin being disengagedfrom the lock recess when said sections are extended to establish saidoperative launcher position, and said member is in its forward position.

7. In a rocket launcher, first and second tubular sections connected totelescope between a shortened, inoperative position and an extended,operative position, one end of said first section being the breech endor" the launcher, and means for firing a rocket positioned in saidlauncher, said means including a firing pin and a firing spring carriedby said first section, said firing spring being connected as to said pinto be loaded by movement of said firing pin into its cocked position,and an element connected to said pin, means connecting said element tosaid second section; a trigger controlled release including a searcarried by said second section, and a movable member conected to saidelement and operative to effect its engagement with said sear, theengagement of said movable member with said sear being ineffective tomove said firing pin into its cocked position in the inoperativeposition of said launcher, said firing pin being then cocked by theextension of said sections to establish said oper ative launcherposition, and releasable means to interlock said sections when extendedto establish said 0 erative launcher position.

8. In a rocket launcher, first and second tubular sections telescopinglyconnected to enable said launcher to be extended from a shortened,inoperative position into an elongated, operative position, one end ofsaid first section being the breech end of the launcher, said firstsection fitting within said second section, and trigger controlled meansfor firing a rocket positioned in said first launcher section andincluding a firing pin connected to said first section for limitedmovement relative thereto between firing and cocked positions, a firingspring tensioned when said firing pin is in said cocked position, and anelement connected to said firing pin and attached to and moving withsaid second section during extending movement of said second sectionrelative to said first section from a partly extended launcher positioninto said operative launcher position thereby to effect said relativemovement of said firing pin to establish a cocked position.

9. In combination, a rocket having an annular shoulder between its endsand a rocket launcher including first and second tubular sectionstelescopingly connected to enable said launcher to be extended from ashortened, inoperative position into an elongated, operative position,one end of said first section being the breech end of the launcher, saidfirst section fitting within said second section with its forward endproviding a shoulder in rearward engagement with the rocket shoulder toprevent rearward movement of said rocket, a lock linking said rocket tosaid first section to hold said rocket against forward movement, saidlock yielding to the force exerted by said rocket when fired, andtrigger controlled means for firing a rocket positioned in said firstlauncher section and including a firing pin connected to said firstsection for limited movement relative thereto between firing and cookedpositions, an igniter, said igniter being connected to and incommunication with the interior of the rocket and including a cap heldby said first section for engagement by said firing pin in its firingposition, a firing spring tensioned when said firing pin is in saidcocked position, and an element connected to said firing pin andattached to and moving wit; said second section during extendingmovement of said second section relative to said first section from apartly extended launcher position into said operative launcher positionthereby to effect said relative movement of said firing pin to establishits co ked position.

10. In combination, a rocket having an annular shoulder between itsends, and a rocket launcher including first and second tubular sectionstelescopingly connected to enable said launcher to be extended from ashortened, inoperative position into an elongated, operative position,one end of said first section being to breech end of the launcher, saidfirst section fitting within said second section with its forward endproviding a shoulder in rearward engagement with the rocket shoulder toprevent rearward movement of said rocket, a lock linking said rocket tosaid first section to hold said rocket against forward movement, saidlock yielding to the force exerted by said rocket when fired, triggercontrolled means for firing a rocket positioned in said first launchersection and including a firing pin connected to said first section forlimited movement relative thereto between firing and cocked positions,an igniter connected to and in communication with the interior of therocket and including a cap held by said first section for engagement bysaid firing pin in its firing position, said launcher also including afiring spring tensioned when said firing pin is in said cocked position,and an element connected to said firing pin and attached to and movingwith said second section during extending movement of said secondsection relative to said first section from a partly extended launcherposition into said operative launcher position thereby to effect saidrelative movement of said firing pin to establish its cocked position,and means to hold said rocket in its shortened position, said holdingmeans including a pair of end covers, a strap having lengthwiseelasticity and including a connection with each of said covers, theconnection between said strap and said breech end cover being a hookdetachably caught on the edge thereof, a pull pin connection 1 0 betweensaid breech cover and said first section opposing the strap resiliency,the connection between said strap and said muzzle end cover applying thestrap resiliency to seat said muzzle cover against said muzzle when thebreech end cover connection is operative, said muzzle cover and saidstrap being freed when said breech cover is open.

References Cited in the file of this patent UNITED STATES PATENTS2,353,885 Fanger et a1. July 18, 1944 2,496,316 Skinner et a1 Feb. 7,1950 2,610,405 Dickinson Sept. 16, 1952 2,788,599 Brandt Apr. 16, 19572,874,501 Koucky et a1 Feb. 24, 1959 2,966,827 Harvey Jan, 3, 19613,021,600 Edstrom Feb. 20, 1962

1. IN A ROCKET LAUNCHER, FIRST AND SECOND TUBULAR SECTIONS CONNECTED TOTELESCOPE BETWEEN A SHORTENED, INOPERATIVE POSITION AND AN EXTENDED,OPERATIVE POSITION, ONE END OF SAID FIRST SECTION BEING THE BREECH ENDOF THE LAUNCHER, AND MEANS FOR FIRING A ROCKET POSITIONED IN SAIDLAUNCHER, SAID MEANS INCLUDING A FIRING PIN AND A FIRING SPRING CARRIEDBY SAID FIRST SECTION, SAID FIRING SPRING BEING CONNECTED TO SAID PIN TOBE LOADED BY MOVEMENT OF SAID FIRING PIN INTO ITS COCKED POSITION, ANDAN ELEMENT CONNECTED TO SAID PIN, MEANS CONNECTING SAID ELEMENT TO SAID